Unsteady body force model for rotating stall in axial compressor with various inlet conditions
Jin Guo 1,2
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COMAC Shanghai Aircraft Design and Research Institute, Shanghai, China
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China
Submission date: 2023-01-19
Final revision date: 2023-09-02
Acceptance date: 2023-09-02
Online publication date: 2023-12-04
Publication date: 2024-01-31
Corresponding author
Jin Guo   

Power System Department, COMAC Shanghai Aircraft Design & Research Institute, China
Journal of Theoretical and Applied Mechanics 2024;62(1):31-45
To analyze the dynamic stall of multistage axial compressors, a three-dimensional unsteady numerical model is established based on the body force model. For a two-stage axial com- pressor with a clean inlet, the calculated maximum steady static pressure rise coefficient is only 0.1% different compared with the experimental data. The characteristic frequency of the dynamic stall evolution basically agrees with the experimental results, which proves the effectiveness of the model. For the compressor with a combined radial-circumferential total pressure inlet distortion, the predictions preliminarily verify the ability of the model for qualitative description of the flow instability process with the complex inlet distortion.
Cao T., Hield P., Tucker P.G., 2017, Hierarchical immersed boundary method with smeared geometry, Journal of Propulsion and Power, 33, 5, 1151-1163.
Creveling H.F., Carmody R.H., 1968, Axial-flow compressor computer program for calculating off design performance, NASA CR, 72472.
Day J., 2016, Stall, surge, and 75 years of research, Journal of Turbomachinery, 138, 1, 011001.
Edwards J.R., 1997, A low-diffusion flux-splitting scheme for Navier-Stokes calculations, Computers and Fluids, 26, 6, 635-659.
Fortin J., Moffatt W.C., 1990, Inlet flow distortion effects on rotating stall, ASME International Gas Turbine and Aeroengine Congress and Exposition, 90-GT-215.
Gallimore S. J., 1986, Spanwise mixing in multistage axial flow compressors: Part II – Throughflow calculations including mixing, Journal of Turbomachinery, 108, 1, 10-16.
Gallimore S.J., Cumpsty N. A., 1986, Spanwise mixing in multistage axial flow compressors: Part I – Experimental investigation, Journal of Turbomachinery, 108, 1, 2-9.
Gong Y., Tan C.S., Gordon K.A., Greitzer E.M., 1999, A computational model for short-wavelength stall inception and development in multistage compressors, Journal of Turbomachinery, 121, 4, 726-734.
Guo J., Hu J., 2018, A three-dimensional computational model for inlet distortion in fan and compressor, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 232, 2, 144-156.
Hu J., Peters T., Fottner L., 1999, Numerical simulation of flow instabilities in high speed multistage compressors, Journal of Thermal Science, 8, 1, 23-31.
Huang Q., Zhang M., Zheng X., 2019a, Compressor surge based on a 1D-3D coupled method – Part 1: Method establishment, Aerospace Science and Technology, 90, 342-356.
Huang Q., Zhang M., Zheng X., 2019b, Compressor surge based on a 1D-3D coupled method – Part 2: Surge investigation, Aerospace Science and Technology, 90, 289-298.
Jahnen W., Peters T., Fottner L., 1999, Stall inception in a 5-stage HP-compressor with increased load due to inlet distortion, ASME International Gas Turbine and Aeroengine Congress and Exhibition, 99-GT-440.
Johnsen I.A., Bullock R.O., 1965, Aerodynamic design of axial-flow compressors, NASA SP-36.
Longley J.P., 2007, Calculating stall and surge transients, ASME Turbo Expo, Montreal, 125-136.
Mao Y., Dang T., 2020, A three-dimensional body-force model for nacelle-fan systems under inlet distortions, Aerospace Science and Technology, 106, 106085.
Marble F.E., 1964, Three-dimensional flow in turbomachines, [In:] Aerodynamics of Turbines and Compressors. (HSA-1), Vol. 1, William R. Hawthorne (Edit.), Princeton: Princeton University Press
Perovic D., Hall C.A., Gunn E.J., 2019, Stall inception in a boundary layer ingesting fan, Journal of Turbomachinery, 141, 9, 091007.
Righi M., Pachidis V., Könözsy L., Pawsey L., 2018, Three-dimensional through-flow modelling of axial flow compressor rotating stall and surge, Aerospace Science and Technology, 78, 271-279.
Rosa Taddei S., 2021, A novel blade force approach to two-dimensional meanline simulation of transonic compressor rotating stall, Aerospace Science and Technology, 111, 106509.
Uranga A., Drela M., Greitzer E.M., Titchener N.A., Lieu M.K., Siu N.M., Huang A.C., Gatlin G.M., Hannon J.A., 2014, Preliminary experimental assessment of the boundary layer ingestion benefit for the D8 aircraft, 52nd Aerospace Sciences Meeting , AIAA 2014-0906.
Wang M., Sun H., Wang Z., Wang Y., Magagnato F., Luan Y., 2020, Numerical investigation of the effects of system volume and average mass flow on the surge characteristics of an axial compressor, Aerospace Science and Technology, 106, 106172.
Zhang W., Vahdati M., 2020, Stall and recovery process of a transonic fan with and without inlet distortion, Journal of Turbomachinery, 142, 1, 011003.
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